Fuel nozzle for combustor
First Claim
1. A nozzle for a combustor, the nozzle comprising:
- a center body;
a burner tube provided around the center body and defining a fuel-air mixing passage therebetween;
an outer peripheral wall provided around the burner tube and defining an air flow passage therebetween;
a nozzle tip connected to the center body, the nozzle tip comprising;
a pilot fuel passage configured to deliver a flow of pilot fuel to a combustion zone; and
a plurality of transfer passages radially outboard of the pilot fuel passage, the plurality of transfer passages configured to deliver a flow of air for combustion with the flow of pilot fuel in the combustion zone and further configured to deliver a flow of transfer fuel to the combustion zone; and
at least one swirl vane disposed in the fuel-air mixing passage, the swirl vane defining a cooling chamber configured to receive fuel from a premix fuel passage, andwherein the fuel flows from the premix fuel passage through a reverse flow passage into the cooling chamber.
2 Assignments
0 Petitions
Accused Products
Abstract
A nozzle for a combustor is disclosed. The nozzle includes a center body, a burner tube provided around the center body and defining a fuel-air mixing passage therebetween, and an outer peripheral wall provided around the burner tube and defining an air flow passage therebetween. The nozzle further includes a nozzle tip connected to the center body. The nozzle tip includes a pilot fuel passage configured to deliver a flow of pilot fuel to a combustion zone, and a plurality of transfer passages. The plurality of transfer passages are configured to deliver a flow of air for combustion with the flow of pilot fuel in the combustion zone and further configured to deliver a flow of transfer fuel to the combustion zone.
38 Citations
15 Claims
-
1. A nozzle for a combustor, the nozzle comprising:
-
a center body; a burner tube provided around the center body and defining a fuel-air mixing passage therebetween; an outer peripheral wall provided around the burner tube and defining an air flow passage therebetween; a nozzle tip connected to the center body, the nozzle tip comprising; a pilot fuel passage configured to deliver a flow of pilot fuel to a combustion zone; and a plurality of transfer passages radially outboard of the pilot fuel passage, the plurality of transfer passages configured to deliver a flow of air for combustion with the flow of pilot fuel in the combustion zone and further configured to deliver a flow of transfer fuel to the combustion zone; and at least one swirl vane disposed in the fuel-air mixing passage, the swirl vane defining a cooling chamber configured to receive fuel from a premix fuel passage, and wherein the fuel flows from the premix fuel passage through a reverse flow passage into the cooling chamber. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
-
-
9. A combustor for a gas turbine system, the combustor comprising:
a nozzle, the nozzle comprising; a center body; a burner tube provided around the center body and defining a fuel-air mixing passage therebetween; an outer peripheral wall provided around the burner tube and defining an air flow passage therebetween; a nozzle tip connected to the center body, the nozzle tip comprising; a pilot fuel passage configured to deliver a flow of pilot fuel to a combustion zone; and a plurality of transfer passages radially outboard of the pilot fuel passage, the plurality of transfer passages configured to deliver a flow of air for combustion with the flow of pilot fuel in the combustion zone and further configured to deliver a flow of transfer fuel to the combustion zone; and at least one swirl vane disposed in the fuel-air mixing passage, the swirl vane defining a cooling chamber configured to receive fuel from a premix fuel passage, and wherein the fuel flows from the premix fuel passage through a reverse flow passage into the cooling chamber. - View Dependent Claims (10, 11, 12, 13, 14, 15)
Specification